| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Double hinged access panel for aircraft | US14735309 | 2015-06-10 | US10081976B2 | 2018-09-25 | Michael R. Urban |
| An access door assembly includes a door panel located at a door opening and a primary hinge having a primary hinge axis and operably connected to the door panel. A guide track is affixed at the door opening and is operably connected to the door panel to guide rotation of the door panel about the first hinge axis. A secondary hinge having a secondary hinge axis is operably connected to the door panel. The secondary hinge allows for rotation of a first portion of the door panel about the secondary hinge axis, while a second portion of the door panel is stationary. | ||||||
| 102 | Aircraft including a fuselage sponson | US15208970 | 2016-07-13 | US10023295B2 | 2018-07-17 | David Alfano; Guillaume Legras; Jean Nicola |
| An aircraft having a sponson extending substantially transversely relative to a main body of the fuselage of the aircraft and substantially perpendicularly relative to a vertical anteroposterior plane of symmetry P of the main body of the fuselage when the aircraft is standing on a horizontal support, the sponson including a notch locally reducing a cross-section of the sponson in a connection zone of the sponson, the connection zone being suitable for being arranged in the immediate proximity of the main body of the fuselage of the aircraft from which the sponson emerges transversely, the notch being open at least to a front outside face and to a top outside face of the sponson and being suitable for receiving a bottom portion of a sliding side door when in its open position. | ||||||
| 103 | Fibre composite component, winglet and aircraft with a fibre composite component | US14054875 | 2013-10-16 | US09957032B2 | 2018-05-01 | Tobias Kremer |
| A fiber composite component made of a fiber composite material comprises at least one first surface section, at least one second surface section and at least one transition region. The first surface section and the second surface section are arranged at an angle to each other and incorporate the transition region. The transition region comprises at least one first curvature section and at least one second curvature section whose mean curvatures differ from each other, which curvature sections connect to each other in a tangentially continuous manner. The first surface section connects to the transition region, and the transition region connects to the second surface section in each case in a tangentially continuous manner. In one example, the radius of curvature of the first curvature section is smaller than that of the second curvature section. | ||||||
| 104 | Aircraft | US14637561 | 2015-03-04 | US09933073B2 | 2018-04-03 | Shingo Goto; Toshiaki Sugimura |
| An aircraft including: a penetration member that penetrates an airframe between an inside and an outside via an opening provided in the airframe; a seal that seals a gap set between an opening formation member forming the opening and the penetration member; and a retainer that presses the seal against the penetration member and the opening formation member, wherein each of the penetration member and the opening formation member includes a receiving section that receives the seal, both of the receiving sections are arranged along a direction connecting one side and the other side of the gap with the gap therebetween, and the seal is fixed to only one of the receiving section of the penetration member and the receiving section of the opening formation member. | ||||||
| 105 | SYSTEM AND METHOD FOR DEPLOYMENT OF AN AIRCRAFT WEAPONS SYSTEM | US15278730 | 2016-09-28 | US20180086463A1 | 2018-03-29 | Aditya B. Chattopadhyay |
| A device for mounting a weapon system to an aircraft includes an adaptor to couple to an internal structure of the aircraft. The device also include a gun mount and a deployment system. The deployment system is coupled to the adaptor to the gun mount and is configured to move the gun mount from a first position internal to the aircraft to a second position at least partially external to the aircraft. | ||||||
| 106 | Window panel for an airframe and method of producing same | US14469146 | 2014-08-26 | US09902483B2 | 2018-02-27 | Pierre C. Zahlen; Johannes Born; Lars Meyer; Gregor Baumbach; Claus Hanske; Jens Prowe; Johan Oentoro; M. Ichwan Zuardy; Wouter Brok; Martin Metten |
| The present disclosure pertains to a window panel for a body structure of a vehicle, especially an airframe of an aircraft or spacecraft, including a first skin which extends over a first side of the panel to form an outer skin of the vehicle body structure; a second skin which extends over a second side of the panel to form an inner skin of the vehicle body structure; and a core, especially a foam core, located between and covered by the first and second skins in a sandwich structure. The window panel includes at least one window aperture formed through the first layer, the core, and the second layer. The core may be confined to or extends over a limited extent, region or part of the panel. Thus, the first skin and/or the second skin may extend over or cover a greater area of the panel than the core. | ||||||
| 107 | POWERED AIRBAG FOR AEROPLANE'S VERTICAL FALL DURING AN ACCIDENT | US15513566 | 2015-11-20 | US20180009541A1 | 2018-01-11 | Ngoc Quy Pham |
| The invention is about a powered airbag for planes in case of uncontrollable falling which makes the plane fall vertically with the head up. The invention includes the bonnet cover of the head 1, the hinges of the bonnet cover 17, the head cover of the plane 12, the structural frame of the head the plane 13, the container of gas-creating material 8, Valve to activate the airbag 9. There is a difference that the structural frame of the head of the plane 13 has a powered airbag 11, the flexible soft tube 10 which connects the powered airbag 11 to the frame of the head of the plane 13 | ||||||
| 108 | Composite material structure, and aircraft wing and aircraft fuselage provided therewith | US13881590 | 2012-01-26 | US09751608B2 | 2017-09-05 | Yuya Tanaka; Hideyuki Suzuki; Yutaka Kanayama; Kazuki Sato; Masatake Hatano; Satoru Saito; Akihisa Watanabe; Ryo Abe |
| A composite material structure reinforced against stress concentration in peripheral edge portions of holes and enabled to be reduced in weight. A wing (1) is formed in a box structure. A lower surface outer plate (3) of the wing (1) includes: a center section (3b) made of metal extending in one direction and having access holes (5) formed therein; a front section (3a); and a rear section (3c) made of fiber reinforced plastics extending in the one direction and connected to both side portions of the center section (3b). As the metal used for the center section (3b), a titanium alloy or an aluminum alloy is suitable. | ||||||
| 109 | DOOR SYSTEM FOR AN EXHAUST GAS DUCT OF AN AUXILIARY POWER UNIT OF AN AIRCRAFT | US15385405 | 2016-12-20 | US20170183076A1 | 2017-06-29 | Pío FERNÁNDEZ LÓPEZ; Pedro Felipe RAMOS-PAUL LASTRA; Cristina SADUÑO OBREGON; Víctor BARREIRO RODRÍGUEZ; David PULPON BEJAS |
| A door system configured to be attached to the fuselage of a tail cone of an aircraft wherein the tail cone comprises an exhaust gas duct of an auxiliary power unit of the aircraft and an opening of the exhaust gas duct located at the rear part of the tail cone. The door system comprises a door which is movable between an open and a closed position, the door being configured such that, in the closed position, it covers the opening of the exhaust gas duct and that the door being shaped such that it follows the aerodynamic shape of the fuselage of the tail cone in its closed position. | ||||||
| 110 | Aircraft door and aircraft comprising such an aircraft door | US14722267 | 2015-05-27 | US09682765B2 | 2017-06-20 | Carsten Paul; Holger Homann |
| An aircraft door includes an outer shell with an exterior and an interior, a stiffening structure arranged on the interior of the outer shell, and at least one door seal arranged on the interior of the outer shell. The door seal is circumferential in an edge region. In the edge region between the outer shell and the door seal at least one circumferential stiffening component is arranged that is connected to the stiffening structure. Thus, in a particularly simple manner and without modifications to a stiffening structure, an aircraft door may be provided with very substantial stiffness in an edge region. | ||||||
| 111 | GASKET SEAL, DOOR OF AIRCRAFT, SEAL STRUCTURE FOR OPENING PORTION OF AIRCRAFT, AND AIRCRAFT | US15444587 | 2017-02-28 | US20170167611A1 | 2017-06-15 | Yusaku YAHATA; Takashi YOKOI; Keiichiro DOI; Mikishige IBARAGI |
| To reliably prevent entrance of electro-magnetic waves in a door that closes an opening portion formed in an airframe of an aircraft. A gasket seal 20 which is arranged between an opening portion 12 formed in an airframe of an aircraft and a door 13 for closing the opening portion 12, includes: a gasket seal body that is made of a rubber material; and conductive fiber 24 that covers a surface of the gasket seal body. When the door 13 is in a closed state, the gasket seal 20 whose surface is made conductive is abutted against a striker 30 provided on a skin 11 side of the airframe and made of a conductive material. The door 13 and the skin 11 of the airframe are electrically connected together via the conductive fiber 24 and the striker 30, and electro-magnetic waves can be reliably shielded. | ||||||
| 112 | DECOMPRESSION ASSEMBLY WITH AN AIR CHANNEL | US15349244 | 2016-11-11 | US20170144745A1 | 2017-05-25 | Uwe Schneider |
| A decompression assembly for use in an aircraft comprises a cabin lining element, an opening formed in the element, and an air channel arranged adjacent to a rear face of the element and connected to the opening. The air channel is provided with an air outlet which, during normal operation of the assembly, discharges air exiting a cabin region delimited by the element through the opening into an area located between the element and an aircraft outer skin, a first decompression opening, and a first decompression flap which, during normal operation of the decompression assembly, closes the first decompression opening in the air channel and which, in the event of a rapid decompression, opens the first decompression opening to allow a pressure equalization between the aircraft cabin region and the aircraft area located between the cabin lining element and the aircraft outer skin. | ||||||
| 113 | DECOMPRESSION ASSEMBLY WITH TWO DECOMPRESSION OPENINGS | US15349254 | 2016-11-11 | US20170144744A1 | 2017-05-25 | Uwe Schneider |
| An aircraft decompression assembly, comprising a cabin lining element, an element opening and an air channel adjacent to an element rear face and connected to the opening. A channel outlet, during normal assembly operation, discharges air exiting a cabin region delimited by the element through the opening into a secluded area between the element and an aircraft outer skin. A first decompression opening has a first decompression flap, which during normal operation, closes the first decompression opening and, in the event of a rapid decompression, opens the first decompression opening equalizing a pressure between the cabin region and the secluded area. A second decompression opening in the lining element has a second decompression flap which, during normal operation, closes the second decompression opening and which, in the event of a rapid decompression, opens the second decompression opening equalizing a pressure between the cabin region and the secluded area. | ||||||
| 114 | Aircraft door and aircraft comprising the same | US14290257 | 2014-05-29 | US09643730B2 | 2017-05-09 | Ichiro Maeda |
| An aircraft door 18 which closes an opening of a storage space 16 for storing a RAT 13 as an accessory and which is opened in association with deployment of the RAT 13 from the storage space 16, the door including: a door body 20 that opens and closes the opening, and whose front surface faces an outside and whose rear surface faces the storage space 16 in a closed state; and a fence 24 that rises from the rear surface of the door body 20. In a traveling direction of the aircraft, the fence 24 is located anterior to a position where the RAT 13 is stored. The fence 24 prevents an airflow Air from passing through between the RAT 13 and the door body 20 in an initial stage where the door 18 starts to be opened, thereby suppressing the aerodynamic force in the closing direction acting on the door body 20. | ||||||
| 115 | AIRCRAFT INCLUDING A FUSELAGE SPONSON | US15208970 | 2016-07-13 | US20170113781A1 | 2017-04-27 | David ALFANO; Guillaume LEGRAS; Jean NICOLA |
| An aircraft having a sponson extending substantially transversely relative to a main body of the fuselage of the aircraft and substantially perpendicularly relative to a vertical anteroposterior plane of symmetry P of the main body of the fuselage when the aircraft is standing on a horizontal support, the sponson including a notch locally reducing a cross-section of the sponson in a connection zone of the sponson, the connection zone being suitable for being arranged in the immediate proximity of the main body of the fuselage of the aircraft from which the sponson emerges transversely, the notch being open at least to a front outside face and to a top outside face of the sponson and being suitable for receiving a bottom portion of a sliding side door when in its open position. | ||||||
| 116 | EXTERNALLY MOUNTED AUXILIARY DOOR FOR AN AIRCRAFT | US15148434 | 2016-05-06 | US20160325816A1 | 2016-11-10 | Michael J. Scimone |
| A door assembly for mounting on an aircraft includes a rail mounted exteriorly to an outer skin of the aircraft, and a door movably coupled to the rail. The door assembly also includes a motor mountable in an interior of the aircraft, and a shaft extending through a sealed shaft port in the outer skin of the aircraft. The shaft couples the motor to the door, such that the door is movable between a first position and a second position along an outer moldline of the aircraft. | ||||||
| 117 | Device for limiting the deflection on a door arranged in a fuselage cell of an aircraft | US14289690 | 2014-05-29 | US09409641B2 | 2016-08-09 | Ronald Risch |
| The invention relates to a device for limiting the deflection of a door (1), particularly a hatch or a freight door, arranged in a fuselage cell (3) of an aircraft, having at least one holding element (5) arranged preferably in the region of a door jamb (4) or in the region of a door leaf edge (7).In order to ensure deflection limitation for doors, hatches and freight doors in aircraft which can be triggered manually independently of an actuation of the normal locking system, it is proposed according to the invention that the at least one holding element (5) can, if there is a sufficient pressure difference Δp between the internal pressure pi prevailing in the fuselage cell (3) and the outside air pressure pa prevailing outside of the fuselage cell (3), be brought into engagement with at least one abutment (6) arranged in the region of the door leaf edge (7) or the door jamb (4).In addition it is proposed that if there is a sufficiently large pressure difference Δp the at least one holding element (30, 55) is automatically pivoted or can be manually pivoted and can hereby be brought into engagement with the at least one abutment (31, 52). | ||||||
| 118 | APPARATUS AND METHOD FOR FACILITATING BLADDER INSTALLATION AND REMOVAL | US14611357 | 2015-02-02 | US20160221690A1 | 2016-08-04 | Steven L. Smith |
| An apparatus for facilitating fluid bladder removal and installation from a support structure through an access opening includes a frame defining a central opening dimensioned to conform to the access opening, the frame having opposed first and second surfaces and adapted to removably mount either inside or outside the support structure around the access opening, and a plurality of roller assemblies mounted to the first surface around the central opening. The apparatus is connected inside (for removal) or outside (for installation) the support structure with the rollers extending away from and surrounding the access opening to facilitate passage of the fluid bladder. | ||||||
| 119 | HEAT REMOVAL STRUCTURE OF AIRCRAFT MAIN LANDING GEAR BAY | US14973098 | 2015-12-17 | US20160214720A1 | 2016-07-28 | Nobuhide HARA; Tadahiko SUZUTA |
| An aircraft includes: a fairing which covers a lower part of a fuselage having a main landing gear bay (MLG bay), and defines a ventilation cavity communicating with the MLG bay between the fairing and the fuselage; and a heat removal system which removes heat generated from the MLG inside the MLG bay to the outside of the MLG bay by suctioning/discharging air through an inlet port and an outlet port leading from the ventilation cavity or the MLG bay to external air. The fairing defines a wheel opening through which a wheel of the MLG enters and exits, and defines a ventilation port, which functions as one of the inlet and outlet ports, between the fairing and an outer peripheral part of the wheel exposed from the wheel opening to the lower side of the MLG bay when the MLG is retracted. | ||||||
| 120 | QUICK RELEASE HINGE | US14592593 | 2015-01-08 | US20160201371A1 | 2016-07-14 | David Harding; William Heber |
| Aspects of the disclosure are directed to a system configured for installing or removing a door from an aircraft, the system comprising: a pin, a hinge comprising a slot that forms a cavity for rotatively coupling the hinge and the pin, a clamp coupled to the pin, and a retaining mechanism on the clamp that selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged. | ||||||
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